JP3672597B2 - Fuel lance for liquid and / or gaseous fuel - Google Patents

Description

[0001]
[Industrial application fields]
The present invention relates to the field of combustion technology. The present invention is directed to a fuel lance for liquid and / or gaseous fuel inserted into a combustion chamber, such as a fuel lance used in a gas turbine.
[0002]
[Prior art]
In order to inject liquid and / or gaseous fuel into the combustion chamber of the premixing burner, a fuel lance is used that enters the combustion chamber and distributes the fuel appropriately into the combustion air flowing beside it. The
[0003]
When designing such a fuel lance, it is necessary to meet various requirements that are partly due to environmental conditions and partly due to imposed requirements.
[0004]
That is, the combustion air flowing by the fuel lance has a temperature that is substantially independent of the fuel flow in the lance. The lance itself and the fuel introduced in the lance must be protected against too high temperatures of the combustion air.
[0005]
When the combustion chamber is operated between full load and partial load with a high fuel ratio, the fuel is provided in an appropriate distribution in any operating state, supplied to the combustion air stream in the same manner, and Care must be taken to be mixed. Since burner aerodynamics is practically independent of fuel, both gaseous and liquid fuel must be able to be injected into the combustion air stream in the same manner in order to achieve proper combustion.
[0006]
We want the lance to use as little transport or auxiliary air as possible so that the efficiency of the burner is as great as possible.
[0007]
Furthermore, care must be taken to minimize the recycle zone or wake that is formed in the range of the fuel lance and is filled with a gas containing fuel, resulting in a flame backflush or thermoacoustic vibration.
[0008]
When injecting liquid fuel, i.e. when injecting oil, it must be avoided that the finely distributed oil-air mixture is ignited prematurely.
[0009]
In addition, for liquid fuels, harmful deposits must be prevented from forming inside the lance due to the elevated temperature and fuel vaporization. This is because this deposit hinders the operation of the lance in the long run or makes it impossible at all.
[0010]
[Problems of the Invention]
An object of the present invention is to provide a fuel lance that satisfies the above-mentioned requirements, reliably injects gaseous and / or liquid fuel, increases efficiency, and emits less harmful components.
[0011]
[Means for solving the problems]
The subject of the present invention is a fuel lance for liquid and / or gaseous fuel inserted into the combustion chamber,
(A) a liquid fuel pipe extending along the lance axis surrounding the liquid fuel passage for guiding the liquid fuel;
(B) a gas pipe that surrounds the liquid fuel pipe and forms a gas passage for supplying gaseous fuel to and from the liquid fuel pipe;
(C) a lance mantle for enclosing the gas pipe and forming an air passage for guiding cooling or atomizing air to and from the gas pipe;
(D) at least one air / fuel nozzle provided on the side of the downstream end of the fuel lance, for flowing air from the air passage to the combustion chamber surrounding the fuel lance;
(E) at least one gas nozzle disposed in the gas pipe and for allowing gas from the gas passage to flow with the air to the combustion chamber through the air passage and at least one air / fuel nozzle;
(F) at least one liquid fuel nozzle disposed in the liquid fuel pipe and allowing liquid fuel from the liquid fuel passage to flow with the air to the combustion chamber through the air passage and at least one air / fuel nozzle;
The gas pipe and the liquid fuel pipe end in front of at least one air / fuel nozzle in the flow direction, the gas nozzle and the liquid fuel nozzle being arranged at the end of each pipe, Oriented parallel to each other and provided with a loop-shaped guide plate for each air / fuel nozzle and another nozzle, which guides the gas or liquid fuel flow exiting from another nozzle by approximately 90 °. Solved by a fuel lance for liquid and / or gaseous fuel, characterized by turning and introduction into each air / fuel nozzle.
[0012]
The core of the present invention comprises a nozzle device with a suitable lance and a cooling air supply device that encloses the lance in a mantle shape so that the cooling air prevents premature ignition for cooling the lance and fuel. Is to be used for general promotion of. This achieves optimal mixing and combustion that lowers harmful component emissions and increases efficiency. Furthermore, the gas pipe and the liquid fuel pipe end in front of at least one air / fuel nozzle in the flow direction, the gas nozzle and the liquid fuel nozzle being arranged at the end of each pipe and oriented parallel to the lance axis A loop-shaped guide plate is provided for each air / fuel nozzle and another nozzle, the guide plate redirects the gas or liquid fuel flow flowing out of the other nozzle by approximately 90 °, By introducing into the air / fuel nozzle, an air operated atomizer for liquid fuel distribution and mixing is realized. This nebulizer is known as “prefilmigatorizer” by Anglo-Saxon literature (see also AH Lefebure, Airblast Atomization, Prog. Energy Combust. Sci., Vol. 6, S. 233-261 (1980)).
[0013]
The first advantageous embodiment of the fuel lance according to the invention is characterized in that at least one air / fuel nozzle and at least one gas nozzle are arranged in a circle and are arranged one after the other on a common nozzle axis. Is smaller than the diameter of the air / fuel nozzle. The gas stream flowing out of the gas nozzle is surrounded by the jacket-like air stream when the air / fuel nozzle flows as described above. This, on the other hand, gives the gaseous fuel the same injection path as the substantially liquid fuel. On the other hand, since the air flow assists the gas injection almost independently of the amount of gas, the aerodynamic state in the fuel chamber hardly changes even when the gas flow is small.
[0014]
A particularly simple and uniform flow condition in the lance and in the nozzle is that the liquid fuel nozzle is placed on a common nozzle axis along with both other nozzles, as in the second embodiment of the invention. This is achieved for various fuels if the diameter is smaller than the diameter of the gas nozzle and the liquid fuel tube and the gas tube are fixedly connected to the lance mantle in the area of the nozzle. In this case, the fixed connection between the inner tube and the lance mantle serves to keep the mutual position of the nozzles from changing substantially during thermal expansion.
[0016]
According to another advantageous embodiment of the invention, an air passage is guided around the downstream end of the fuel lance, in which at least one auxiliary, oriented substantially parallel to the lance axis. A nozzle is provided, through which air flows out from the air passage to the combustion chamber. Air that does not contain fuel is injected into the space behind the lance tip by the auxiliary nozzle, preventing the formation of recycle zones and / or recycle zones containing fuel at these problematic locations.
[0017]
The method of operating the fuel lance of the present invention is characterized by the fact that air that reaches temperatures up to several hundred degrees Celsius but lower than 600 degrees Celsius passes through the air passages to cool the lance and to distribute fuel. It is led to the nozzle, where it is blown into the combustion chamber as a cannula surrounding the fuel flow. As a result, reliable cooling of the lance is achieved even when the temperature of the combustion air stream or the combustion gas scrubbing by the lance is high.
[0018]
Other embodiments of the fuel lance according to the invention as well as other embodiments of the operating method according to the invention are described in the dependent claims.
[0019]
【Example】
FIG. 1 shows a side view of a fuel lance arranged in a combustion chamber 2 restricted by a casing 3 of a gas turbine or the like (in this case only one part is shown). Not) The fuel lance 1 is in this case arranged on the central axis of the combustion chamber 2 at the lance axis 5 so that hot combustion air flows around it (see the three long arrows in FIG. 1). Accordingly, the fuel lance 1 is adapted to the aerodynamic state of the combustion chamber 2 and is preferably fluidly configured. The fuel lance 1 is surrounded by an elongated lance mantle 11 and is fixed to the casing 3 by a holding arm 4 projecting sideways. The holding arm 4 is likewise preferably fluidly configured and has a wing-like holding arm profile 14 in the illustrated crossing.
[0020]
A plurality of tubes extend through the holding arm 4 and the fuel lance 1 itself, as evidenced by the lance portion shown partially broken in FIG. Through these tubes, gaseous or liquid fuel and cooling or atomizing air are directed to the lance tip located downstream, where appropriate air / fuel nozzles 12 and auxiliary nozzles 13 in the manner described below. And is injected into the combustion chamber 2. The tube includes an axially extending liquid fuel tube 7 located on the inside and a gas tube 9 concentrically surrounding the liquid fuel tube 7. The gas pipe 9 itself is concentrically surrounded by a lance mantle 11 at intervals. Three passages are formed by concentrically arranging the tube and the outer jacket at a distance. That is, the inner liquid fuel passage 6, the gas passage 8 and the air passage 10. The passage functions in various ways depending on the operating mode of the fuel lance 1. These functions will be described hereinafter on the basis of three advantageous embodiments shown in FIGS.
[0021]
In FIG. 2, the lance tip of the fuel lance of the reference example is shown in a longitudinal sectional view. The lance tip is divided into two separate halves to illustrate different operating examples. The upper half is mainly related to the operation example using gaseous fuel with the entered flow (indicated by arrows), and the lower half is mainly related to the operation example using liquid fuel. Correspondingly, the drawing divided in two is selected in the other figures, FIGS. 3 and 4, for the same reason.
[0022]
At the tip of the lance, the inner liquid fuel pipe 7, the gas pipe 9, and the lance mantle 11 come from the left. The gas pipe 9 transitions to a hemispherical pipe head 17 at the end, and the pipe head 17 closes the pipe. The liquid fuel pipe is welded or brazed to the inner surface of the pipe head 17 at the end face and closed in this manner. Since the lance mantle 11 surrounds the tube head 17 in the form of a hemispherical shell at an interval, the air passage 10 formed between the lance mantle 11 and the gas pipe 9 reaches very close to the tip of the lance. The head 17 is surrounded from the outside. A plurality of connecting webs 16 are welded or brazed between the tube head 17 and the hemispherical shell in front of the lance mantle 11. In this way, both tubes 7 and 9 and the lance mantle 11 form a fixed and united unit which is stable in the area of the lance tip. The unit prevents movement between tubes due to thermal expansion.
[0023]
In the range of the tube end, a plurality (preferably four) nozzle sets are provided. The nozzles of these nozzle sets are each disposed on a nozzle shaft 24 that extends perpendicularly (or inclined) to the lance axis 5. The nozzle sets are distributed around the fuel lance 1 in numbers and angular intervals so that the nozzle sets avoid a wake under a predetermined secondary design of the combustion chamber flow and ensure good mixing. Each nozzle set includes a liquid fuel nozzle 18 inserted into the liquid fuel pipe 7, a gas nozzle 15 inserted into the gas pipe, and an air / fuel nozzle 12 inserted into the lance mantle 11. Each nozzle 12, 15, 18 is preferably circular. The diameters of these nozzles 12, 15, 18 are gradual, with the inner liquid fuel nozzle 18 having the smallest diameter and the outer air / fuel nozzle 18 having the largest diameter. The number and diameter of the liquid fuel nozzles 18 are adjusted to the normally generated liquid fuel flow rate. In this case, care must be taken so that the nozzle diameter is too small and the nozzle does not clog when solid deposits are formed. Furthermore, the number of fuel flows injected through the nozzles into the combustion chamber is not too large, impeding aerodynamics around the fuel lance 1 so that the after-flow containing fuel formed behind the lance does not increase. It is necessary to make it.
[0024]
In the case of the operating example with pure gas injection shown in the upper half of FIG. 2, the inner liquid fuel passage 6 is not used at all. The combustible gas flows through the gas passage 8 and the gas nozzle 15 where it forms a radially outwardly directed gas flow through the air / fuel nozzle 12 and into the combustion chamber 2. At the same time, cooling air is supplied through the air passage 10 to a temperature of several hundred degrees Celsius, preferably lower than 600 degrees Celsius. This cooling air likewise exits radially from the air / fuel nozzle into the combustion chamber and surrounds the initial gas flow in a mantle shape. The cooling air has a plurality of functions. That is, the cooling air cools the lance mantle 11 and further forms a thermal protective mantle for the fuel passages inward. In other respects, the cooling air produces a stable, unchanging air flow at the air / fuel nozzle 12 regardless of how much gas is supplied through the lance. Therefore, even when the flow amount of the gaseous fuel is small, the composition of the injection amount hardly changes. In addition, the relatively cool air mantle allows and aids sufficiently long mixing between the combustion air in the combustion chamber 2 and the gaseous fuel necessary for effective combustion. This is because early self-ignition of the air-fuel mixture is surely avoided.
[0025]
In the example of operation with liquid fuel injection shown in the lower half of FIG. 2, liquid fuel, usually an oil-water emulsion, is led to the liquid fuel nozzle 18 through the inner liquid fuel passage 6, There, it is injected radially outward as a liquid fuel flow. In this case, air is supplied through the gas passage 8, this air flows out through the gas nozzle 15, and droplets of liquid fuel are also obtained by alternating action with the liquid fuel flow injected through the gas nozzle 15. Spray-jet airblast atomization. The atomizing stream is surrounded by the cooling air mantle (which also contributes to atomization) in the air / fuel nozzle 12 as described above and is finally injected into the combustion chamber 2. In addition to cooling by air flowing in the air passage 10, an additional thermal shielding step is provided by auxiliary air in the gas passage. As a result, the liquid fuel in the liquid fuel pipe 6 reaches a temperature at which solid deposition is reliably avoided.
[0026]
As can be seen from the above description, the cooling or auxiliary air in the lance has multiple functions simultaneously. Cooling or auxiliary air cools the lance and protects the fuel passage located inside against too high temperatures. Cooling or auxiliary air cools the fuel stream during injection and thus delays its heating, so that sufficient mixing with the combustion air occurs before self-ignition. Cooling or auxiliary air provides the necessary atomization of liquid fuel as auxiliary air. Cooling or auxiliary air assists in mixing the fuel flow in the combustion chamber as a sluice when exiting the air / fuel nozzle 12. The cooling or auxiliary air flow maintains the jet flow out of the nozzle set even when the fuel flow is low.
[0027]
In all these processes, the special arrangement of the nozzles 12, 15, 18 always gives the same aerodynamic configuration, regardless of whether gaseous or liquid fuel is used. That is, the fuel flow is injected into the combustion chamber 2 in the same manner. Since the tubes 7 and 9 are stably coupled to each other and to the lance mantle 11, the uniaxial arrangement of the nozzle set is maintained even when thermal stresses are present on the lance due to various temperature distributions. .
[0028]
The air from the air passage 10 has a further function in an advantageous manner. That is, in the flow direction, a posterior flow containing fuel is formed in principle behind the lance tip for fluid technical reasons. This results in a flame backflash or acoustic vibration (pulsation). Such a phenomenon is unacceptable as it loads the combustion chamber and leads to particularly high harmful component emissions. In order to prevent these, an auxiliary nozzle 13 is provided at the tip of the lance, preferably at the center of the lance axis 5, and an air flow free from combustion passes through the auxiliary nozzle 13 from the air passage 10 to the inside. It is injected into the part of the firing chamber behind the tip. At the same time, this measure achieves cooling of the fuel lance to the forefront.
[0029]
FIG. 3 shows another configuration of the fuel lance of the reference example. In this case, FIG. 3A corresponds to the depiction in FIG. 2, and FIG. 3B is a cross-sectional view taken along line AA in FIG. In this case, the range having the liquid fuel nozzle 18 is shown as being rotated about the lance axis 5 in FIG. The illustrated embodiment differs from the embodiment of FIG. 2 in particular with respect to the placement of the liquid fuel nozzle 18. In this case, the nozzle 18 is not long disposed on the common nozzle axis 24 together with the other nozzles 12 and 15, but is moved backward away from the tip of the lance and at the same time the lance axis 5 is It is rotated as a center (B in FIG. 3). Accordingly, the liquid fuel flow flowing out from the nozzle 18 does not flow out directly through both the other nozzles 15 and 12 for a long time. In this case, the stationary position of the liquid fuel nozzle 18 with respect to the other air / fuel nozzles 12, 15 is no longer necessary, so that the liquid fuel tube 7 can already terminate before the tube head 17, There is no need to be fixed.
[0030]
Another difference from the reference example of FIG. 2 is that each gas nozzle 15 is fitted with one guide pipe 19, and this guide pipe 19 enters the air / fuel nozzle 12 through the air passage 10 from the gas nozzle 15. It is that you are. This makes the formation of the cannula already described effective and allows the gas flow flowing through the guide tube 19 to reach the combustion chamber 2 with relative protection when leaving the air / fuel nozzle 12. .
[0031]
In the upper partial view of FIG. 3A, as in FIG. 2, an example of operation using gaseous fuel is shown. In this case, the liquid fuel pipe 7 is empty and not used. In this case, the jet flow is formed in exactly the same manner as in FIG. In the lower partial view, an operation example using liquid fuel is shown. That is, the liquid fuel flows out from the liquid fuel nozzle 18 as an injection flow and is taken along the inner wall of the gas pipe 9 to the gas nozzle 15 by the auxiliary air sent through the gas passage 8, where the guide pipe together with the auxiliary air. 19 is injected. At the same time, nebulization is performed (air assist atomizer). In this case, the additional ring lamellae 20 on both sides of the liquid fuel nozzle 18 improve the flow condition.
[0032]
The configuration of the fuel lance of the present invention is shown in FIG. 4A corresponds to A in FIG. 2 or FIG. 3, whereas in FIG. 4B, in the flow direction, the special shape of the guide sheet used, the guide sheet and the nozzle Are shown to cooperate. In the case of the configuration of FIG. 4, the air / fuel nozzle 12 is located at the same location as in the embodiment of FIGS. In contrast to this, the arrangement of other nozzles is clearly different. The gas pipe 9 and the liquid fuel pipe 7 have already ended in front of the air / fuel nozzle 12 in the flow direction. A gas nozzle 15 and a liquid fuel nozzle 12 assigned to each air / fuel nozzle 12 are located at the end of each pipe (9 or 7) and are oriented parallel to the lance axis 5. A blade-shaped guide thin plate 22 is provided for each air / fuel nozzle 12 and the nozzles 15 and 18 assigned thereto. The guide thin plate 22 turns the gas or liquid fuel flow flowing out from the nozzles 15, 18 assigned to the guide thin plate 22 by approximately 90 °, and introduces it into the respective air / fuel nozzles 12. As can be seen from FIG. 4B, the guide thin plate 22 is arranged around the lance axis 5 like a clover leaf.
[0033]
Each guide lamina 22 preferably forms a lamina ring 23 which is closed in the area of the air / fuel nozzle 12. The diameter of the thin plate ring 23 is smaller than the diameter of the air / fuel nozzle 12. The diverted flow flowing out of the associated nozzles 15, 18 in this way, when flowing out of the air / fuel nozzle 12, is also surrounded by the air flow in this case. A guide tube 19 is additionally fitted in each gas nozzle 15 so that a reliable change of the gas flow by the guide thin plate 22 can be ensured. Since the guide sheet 22 is fixedly connected to the lance mantle 11 in the range of the nozzles (12, 15, 18), these nozzles cannot move relative to the air / fuel nozzle 12. The coupling is effected via a hemispherical shell-like tube head 21 which corresponds to the tube head 17 of FIG. 2 or 3 and is fixed to the lance mantle 11 with the coupling web 16 already described.
[0034]
In the upper partial view of FIG. 4, the liquid fuel pipe 7 is not used in this case as well. In this case, the gas flow exits from the gas passage 8 through the guide tube 19, is redirected by the guide lamina 22, is focused by the lamina ring 23, passes through the air / fuel nozzle 12, and is enveloped by the air stream. It is surrounded and injected into the combustion chamber. In the case of the liquid fuel operation shown in the lower partial view, the gas passage 8 is not used. That is, the liquid fuel flow flowing out from the liquid fuel nozzle 18 is guided to the air / fuel nozzle 12 along the inner wall of the guide thin plate 22 as a liquid fuel film without auxiliary air, and fine droplets are peeled off at the outer edge of the thin plate ring. To be atomized by a prefilmer atomizer.
[0035]
FIG. 5 shows another reference example of the fuel lance. In this reference example, only the liquid fuel nozzle 18 and the appropriate air / fuel nozzle 12 are located on the nozzle axis 24. The gas nozzle 15 is arranged in front of the nozzles 18 and 12 when viewed in the flow direction regardless of the nozzles 18 and 12 described above. In the case of gas operation (the upper half of the figure), the gas is already strongly mixed with the cooling air in the air passage 10 in front of the air / fuel nozzle 12. The gas-air mixture is injected through the air / fuel nozzle 12 into the combustion chamber. In this case, the air tube 20 emanating from the gas nozzle 15 and extending by the gas nozzle guides cooling air containing no fuel to the head range of the lance. Then, the cooling air is injected into the combustion chamber through the auxiliary nozzle 13 in order to prevent the back flow. In the case of liquid fuel operation (lower half of FIG. 5), liquid fuel flows from the liquid fuel nozzle 18 located in the pipe head 17 through the air pipe 20 directly to the air / fuel nozzle 12, Therefore, as already described, it cooperates with the cooling air from the air passage 10.
[0036]
Overall, according to the present invention, gaseous and liquid fuels can be injected with the same aerodynamic configuration, which works reliably even when the combustion gas temperature is high, enabling good atomization of the liquid fuel and being delayed. A fuel lance that can reduce harmful component emissions by the mixing process is obtained.
[Brief description of the drawings]
FIG. 1 is a side view of a fuel lance disposed in a combustion chamber.
FIG. 2 is a longitudinal sectional view of the tip of a first reference example of a fuel lance (upper half shows operation using gaseous fuel, and lower half shows operation using liquid fuel).
FIG. 3 is a longitudinal sectional view (A) and a transverse sectional view (B) of a second reference example of a fuel lance.
FIG. 4 is a longitudinal sectional view (A) of a fuel lance according to the present invention and a view (B) showing a guide thin plate.
FIG. 5 is a view showing a reference example in which a gas nozzle is arranged in front of another nozzle in the flow direction.
[Explanation of symbols]
1 fuel lance, 2 combustion chamber, 3 casing, 4 holding arm, 5 lance axis, 6 liquid fuel passage, 7 liquid fuel pipe, 8 gas passage, 9 gas pipe, 10 air passage, 11 lance mantle, 12 air / fuel nozzle , 13 auxiliary nozzle, 14 holding arm profile, 15 gas nozzle, 16 coupling web, 17, 21 tube head, 18 liquid fuel nozzle, 19 guide tube, 20 guide tube, 22 guide thin plate, 23 thin plate ring, 24 nozzle axis

Claims (6)

In a fuel lance for liquid and / or gaseous fuel inserted into the combustion chamber (2),
(A) a liquid fuel pipe (6) extending along the lance axis (5) surrounding the liquid fuel passage for guiding the liquid fuel;
(B) a gas pipe (9) that surrounds the liquid fuel pipe (7) and forms a gas passage for supplying gaseous fuel to and from the liquid fuel pipe (7);
(C) a lance mantle (11) surrounding the gas pipe (9) and forming an air passage (10) for guiding cooling or atomizing air to and from the gas pipe (9);
(D) at least one air / flow which is provided on the side of the downstream end of the fuel lance (1) and allows air to flow from the air passage (10) to the combustion chamber (2) surrounding the fuel lance (1). A fuel nozzle (12);
(E) Arranged in the gas pipe (9), gas from the gas passage (8) passes through the air passage (10) and at least one air / fuel nozzle (12) with the air to the combustion chamber (2). At least one gas nozzle (15) to be discharged;
(F) a liquid chamber (7) disposed within the liquid fuel pipe (7) for passing the liquid fuel from the liquid fuel passage (6) with the air through the air passage (10) and at least one air / fuel nozzle (12); at least one liquid fuel nozzle to flow out to 2) and (18),
Have
A gas pipe (9) and a liquid fuel pipe (7) end in front of at least one air / fuel nozzle (12) in the flow direction, and a gas nozzle (15) and a liquid fuel nozzle (18) 9 or 7) , oriented parallel to the lance axis ( 5) and looped for each air / fuel nozzle (12) and another nozzle (15, 18) A guide plate (22) is provided, which guides the gas or liquid fuel flow flowing out of another nozzle (15, 18) by approximately 90 ° and introduces it into each air / fuel nozzle (12). To
A fuel lance for liquid and / or gaseous fuel, characterized in that The guide plate forms a thin plate ring (23) closed in the range of the air / fuel nozzle (12), and the diameter of the thin plate ring (23) is smaller than the diameter of the air / fuel nozzle (12). deflected by flow from the nozzle (15, 18) of the is adapted to be surrounded jacket shape by the air flow when flowing out of the air / fuel nozzle (12), a fuel lance according to claim 1, wherein. A guide tube (19) is additionally press-fitted in the casing (15), and the guide plate (22) is fixedly coupled to the lance mantle (11) in the range of the nozzles (12, 15, 18). The fuel lance according to claim 1 or 2 . Large number of nozzles on the outer periphery of the fuel lance, preferably four nozzles are arranged distributed in accordance with the flow surrounding the fuel lance (1), a fuel lance according to any one of claims 1 to 3 . An air passage (10) is guided around the downstream end of the fuel lance (1), in which at least one auxiliary nozzle (13) oriented substantially parallel to the lance axis is provided. The fuel lance according to any one of claims 1 to 4 , wherein air flows out of the air passage (10) into the combustion chamber (2) through the auxiliary nozzle. The fuel lance (1) is fixed to the casing surrounding the combustion chamber (2) via a lateral holding arm (4) having a holding arm profile (14) suitable for flow, and the pipes (7, 9). ) is inside are brought derived from the combustion chamber (2), a fuel lance according to any one of claims 1 to 5 of the holding arm (4).

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